Compressor blade for an axial compressor

The invention relates to a compressor blade (10) for an axially permeated compressor, preferably of a stationary gas turbine. According to the invention, the skeleton line (32) of the blade tip side profile (30) of the blade (12) of the compressor blade (10) comprises at least two inflection points...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	CORNELIUS CHRISTIAN, NICKE EBERHARD, KROEGER GEORG
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ARTCOLLECTIONS [XRACs] AND DIGESTS WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a compressor blade (10) for an axially permeated compressor, preferably of a stationary gas turbine. According to the invention, the skeleton line (32) of the blade tip side profile (30) of the blade (12) of the compressor blade (10) comprises at least two inflection points (36, 38) for reducing radial gap losses. By means of two inflection points (36, 38) there is a concavely designed suction side contour segment (D) in a segment from 35% to 50% for the suction side contour (42), and a convexly implemented pressure side contour segment (E) for the pressure side contour (40). It is possible by means of said geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor comprising said compressor blades (10).